The objectives of this work were to develop a procedure for predicting and evaluating the performance of engine inlet anti-icing systems for compliance with FAR 25 ice protection requirements without conducting flight tests in natural icing conditions. This must include consideration of water droplet impingment, collection efficiency, internal and external heat transfer, and mass transfer of the impinging water. The method of approach for developing these procedures was to survey current analysis methods involving physical theory and empirical methods and then to develop a computerized model for use in anti-icing system performance analysis. Icing wind tunnel tests were conducted using a three-dimensional nacelle test model to aid in the procedure development. A typical engine-inlet anti-icing system was evaluated with the computer model in a variety of icing environments and operational conditions and compared with icing wind tunnel test results. Correlation between performance predictions and wind tunnel test results was found to have good agreement within the spectrum of conditions that were practicable in the wind tunnel. (Author)

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